US20120171056A1 - Motorcompressor unit with variable aerodynamic profile - Google Patents
Motorcompressor unit with variable aerodynamic profile Download PDFInfo
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- US20120171056A1 US20120171056A1 US13/339,389 US201113339389A US2012171056A1 US 20120171056 A1 US20120171056 A1 US 20120171056A1 US 201113339389 A US201113339389 A US 201113339389A US 2012171056 A1 US2012171056 A1 US 2012171056A1
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- Prior art keywords
- impeller
- compression
- unit according
- diffuser
- regulating member
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/51—Inlet
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
Definitions
- the invention relates to centrifugal motorcompressor units and, more particularly, to centrifugal compressor units of the integrated type in which the compressor and a motor means of driving the compressor are mounted in a common casing that is sealed against the gas handled by the compressor.
- a conventional integrated compressor unit comprises a motor means, generally consisting of an electric drive motor, and a centrifugal compressor comprising one or more compression stages depending on the application.
- Each compression stage comprises a bladed impeller mounted on a driven shaft driven by a rotor which is itself driven by the motor.
- a motor external to the casing is then used to operate the mechanical device that controls the orientation of the vanes.
- Such an arrangement entails making holes in the body of the rotary machine and the consequential use of sealing devices.
- providing holes in the casing of a compressor considerably limits the range in which the compressor can be used, which range remains dedicated to low, or sometimes medium, pressures, which means to say pressures of below around 20 bar.
- the invention therefore proposes a compressor unit comprising at least one motor driving the rotation of a rotor and at least one compression stage comprising a set of bladed impellers mounted on a driven shaft the rotation of which is driven by the rotor, the ensemble comprising the motor and the or each compressor being mounted in a common casing that is gastight with respect to the gas handled by the compressor unit.
- At least one of the compression stages comprises at least one aerodynamic member for regulating the angle of incidence of the flow of gas through the said stage and a motor for controlling the said regulating member mounted in the common casing.
- the regulating member is able to vary the flow angle of gas arriving at a bladed impeller, or leaving a bladed impeller.
- the member is capable of varying the angle of incidence of the flow of gas arriving at at least one bladed impeller.
- the member is capable of varying the flow angle of gas leaving a bladed impeller, for example progressing towards a diffuser.
- the motor that controls the aerodynamic member is incorporated into the casing, the holes in the casing through which the mechanical regulating member passes can be dispensed with, so that the casing therefore remains sealed allowing the motorcompressor unit to operate at higher pressures.
- the operating range of the motorcompressor unit could be extended out to values of the order of 60 to 80 bar.
- the regulating member comprises a vane arranged across a diameter of a gas passage in the compression stage.
- the regulating member may for example comprise a number of radial vanes, each of a length shorter than or equal to half the diameter of the gas passage.
- the vanes can thus be actuated simultaneously for example by mechanical devices such as one or more crown gears driven by devices of the worm type.
- the regulating member is configured so that it is possible to obtain at least three different angles of incidence or of departure of gaseous flow towards a bladed impeller or from a bladed impeller.
- the motorcompressor unit comprises between one and three compression stages, preferably one compression stage, at least one of the said stages being provided with the regulating member.
- the compressor unit comprises several compression stages
- Each regulating stage comprises, in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser.
- the regulating member may then be positioned upstream of the bladed impeller.
- it may be arranged in the diffuser.
- Another variant involves simultaneously installing a regulating member upstream of the compression stage and a regulating member in the diffuser.
- the motorcompressor unit further comprises an electronic control unit external to the casing and connected to the control motor by supply and control cables that pass through the casing at fluidtight lead-throughs.
- FIG. 1 is a schematic view showing the overall design of a single-stage compressor unit
- FIG. 2 is a detailed view of the compressor unit of FIG. 1 , showing the aerodynamic regulating member
- FIG. 3 illustrates an embodiment variant of the compressor unit of FIG. 2 ;
- FIG. 4 is a curve showing the change in power and work developed by the compressor unit as a function of the admitted gas flow rate.
- the motorcompressor unit illustrated in FIG. 1 essentially comprises a motor 1 , consisting for example of a variable-speed electric motor driving the rotation of a rotor 2 , which itself at the same speed drives a driven shaft 3 on which a bladed impeller 4 is mounted.
- a motor 1 consisting for example of a variable-speed electric motor driving the rotation of a rotor 2 , which itself at the same speed drives a driven shaft 3 on which a bladed impeller 4 is mounted.
- the motorcompressor unit thus comprises a single compression stage consisting of the centrifugal bladed impeller 4 which draws in a gas which is delivered from a supply pipe 5 in order to increase its pressure and deliver it at outlet 5 ′.
- the rotor 2 is supported by two end bearings 6 and 7 .
- the rotor 2 and the driven shaft 3 are connected by a flexible coupling 10 .
- the arrangement depicted is advantageous because it considerably simplifies the assembly of the compressor unit by, in particular, eliminating the problems of aligning the rotor with the driven shaft.
- the motorcompressor unit is also provided with a thrust bearing 11 that limits the axial movement of the driven shaft 3 under the action of the rotation of the impeller 4 .
- the assembly which means to say the motor 1 and the compression stage, is arranged in a common casing 12 which is sealed against the gas handled by the compressor.
- the motor 1 here is at the intake pressure of the motorcompressor unit.
- FIG. 2 depicts a detailed view of the motorcompressor unit of FIG. 1 .
- This figure shows the gas intake orifice 5 via which the gas to be compressed is drawn in in the direction of the arrow F, and the impeller 4 which actually compresses the gas in order to deliver it, downstream, to a diffuser D in which the gas is slowed down in order to increase its pressure before it is delivered at outlet.
- the compressor Upstream of the impeller 4 , the compressor is provided with a regulating member, referenced 13 , produced in the form of a vane mounted across a diameter of a gas passage 14 running between the intake orifice 5 and the impeller 4 .
- This vane constitutes an aerodynamic element which makes it possible to control the angle of the flow and keep it optimum over a wide range of flow rates.
- this vane 13 is mounted on a control rod 15 which is turned by a control motor 16 , for example a stepping motor incorporated into the motorcompressor, which means to say arranged inside the common casing 12 .
- the motor 16 is electrically powered from outside the motorcompressor and is operated by a central control unit (not depicted) which causes the motor to turn and accordingly orients the vane 13 in the passage 14 in such a way as to shift the operating curve of the motorcompressor.
- the supply and control cables that connect the control motor and the central control unit pass through the casing 12 at lead-throughs (not depicted) that are sealed against the gas handled by the motorcompressor in such a way as to maintain a level of sealing that is far superior to the seals required at the penetrations for the mechanical devices according to the state of the art, when the motor is located outside the casing.
- the compression stage comprises, in succession, between the inlet 5 and the outlet 5 ′, a supply zone A, the centrifugal impeller 4 and the diffuser D.
- the aerodynamic member 13 here is positioned upstream of the impeller 4 . It would also be possible, according to the variant illustrated in FIG. 3 , for it to be situated in the region of the diffuser.
- FIG. 4 which depicts the change in work developed by the compressor (curves a, b, c) on the one hand, and in the performance (curves a′, b′ and c′) on the other, as a function of the flow rate admitted at inlet to the motorcompressor unit, it is possible to maximize the aerodynamic performance of the compressor by using the variable pitch setting thereby enjoying a wider range of flow rates.
- the motor 1 and the compression stage 3 are arranged in one and the same casing 12 that is sealed against the gas being handled, which means that the inside of the motorcompressor unit, particularly the motor 1 and at least the compression stage 3 , are immersed in the gas that is being handled, at the pressure of the gas entering via the supply pipe 5 .
- the inside of the motorcompressor has no shaft output sealing packing because the shafts bearing the motor 1 and bearing the bladed impeller 4 , and the bearings that support them, are fully contained within the casing.
- the motorcompressor unit has only rotary seals subjected to small pressure differences, for example seals of the labyrinth seal type.
- One particularly advantageous application of the invention is in gas transfer stations in which the pressure ratios that have to be developed between the intake and delivery sides are relatively small, notably below 2, and for which the motorcompressor units are preferably single-stage units or, in general, comprise fewer than three stages. Specifically, for this type of application, it is often desirable to have a relatively wide range of flow rates so that small or large flow rates can be offered.
- an aerodynamic member for controlling the angle of incidence of the gas flow is advantageous for motorcompressor units comprising from 1 to 3 compression stages.
- a member may advantageously be installed in single-stage motorcompressor units.
- the aerodynamic member can be mounted either on the first compression stage or on all the stages.
- the aerodynamic member can be mounted either at the inlet to the compression bladed impeller, so as to modify the angle of incidence of the gas flow handled by the bladed impeller, or at the diffuser so as to modify the deceleration of the gas and thereby modify the operating range. It is also possible, according to another embodiment, to provide one aerodynamic regulating member upstream or at the inlet of the bladed impeller or, in other words, upstream of the compression stage, and one regulating member in the diffuser.
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- Engineering & Computer Science (AREA)
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- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
This motorcompressor unit comprises at least one motor driving the rotation of a rotor and at least one compression stage comprising a set of bladed impellers mounted on a driven shaft the rotation of which is driven by the rotor, the assembly consisting of the motor and the or each compressor being mounted in a common casing that is gastight with respect to the gas handled by the compressor unit.
At least one of the compression members comprises at least one aerodynamic member (13) for regulating the angle at which the gas handled by the said stage flows and a motor (16) for controlling the regulating member (13) mounted in the common casing.
Description
- This application claims priority to French application Ser. No. FR 1061391, filed Dec. 31, 2010, the entire disclosure of which is incorporated herein by this reference.
- The invention relates to centrifugal motorcompressor units and, more particularly, to centrifugal compressor units of the integrated type in which the compressor and a motor means of driving the compressor are mounted in a common casing that is sealed against the gas handled by the compressor.
- A conventional integrated compressor unit comprises a motor means, generally consisting of an electric drive motor, and a centrifugal compressor comprising one or more compression stages depending on the application.
- Each compression stage comprises a bladed impeller mounted on a driven shaft driven by a rotor which is itself driven by the motor.
- In certain applications, and in particular for low-pressure applications, it has been proposed for use to be made of blades with variable pitch vanes so as to modify the work developed by the compression stage to suit the gas flow rate.
- In order to modify the orientation of the vanes, use is made of mechanical devices, for example by fitting the vanes with crown gears driven by worm-type devices.
- A motor external to the casing is then used to operate the mechanical device that controls the orientation of the vanes. Such an arrangement entails making holes in the body of the rotary machine and the consequential use of sealing devices. Now, providing holes in the casing of a compressor considerably limits the range in which the compressor can be used, which range remains dedicated to low, or sometimes medium, pressures, which means to say pressures of below around 20 bar.
- It is an object of the invention therefore to alleviate this disadvantage and to propose an integrated motorcompressor unit with variable aerodynamic profile, which means to say one capable of modifying the flow of gas within the compression stages, and of doing so over a broader range of pressures.
- The invention therefore proposes a compressor unit comprising at least one motor driving the rotation of a rotor and at least one compression stage comprising a set of bladed impellers mounted on a driven shaft the rotation of which is driven by the rotor, the ensemble comprising the motor and the or each compressor being mounted in a common casing that is gastight with respect to the gas handled by the compressor unit.
- According to one general feature of this compressor unit, at least one of the compression stages comprises at least one aerodynamic member for regulating the angle of incidence of the flow of gas through the said stage and a motor for controlling the said regulating member mounted in the common casing. For preference, the regulating member is able to vary the flow angle of gas arriving at a bladed impeller, or leaving a bladed impeller. According to one first embodiment alternative, the member is capable of varying the angle of incidence of the flow of gas arriving at at least one bladed impeller. According to another embodiment variant, the member is capable of varying the flow angle of gas leaving a bladed impeller, for example progressing towards a diffuser.
- Because the motor that controls the aerodynamic member is incorporated into the casing, the holes in the casing through which the mechanical regulating member passes can be dispensed with, so that the casing therefore remains sealed allowing the motorcompressor unit to operate at higher pressures.
- It has been found in particular that, thanks to such an arrangement, the operating range of the motorcompressor unit could be extended out to values of the order of 60 to 80 bar.
- According to another feature, the regulating member comprises a vane arranged across a diameter of a gas passage in the compression stage. The regulating member may for example comprise a number of radial vanes, each of a length shorter than or equal to half the diameter of the gas passage. The vanes can thus be actuated simultaneously for example by mechanical devices such as one or more crown gears driven by devices of the worm type. For preference, the regulating member is configured so that it is possible to obtain at least three different angles of incidence or of departure of gaseous flow towards a bladed impeller or from a bladed impeller.
- According to yet another feature, the motorcompressor unit comprises between one and three compression stages, preferably one compression stage, at least one of the said stages being provided with the regulating member.
- When the compressor unit comprises several compression stages, provision may be made for the flow to be modified by means of an aerodynamic member provided at each stage.
- Each regulating stage comprises, in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser. The regulating member may then be positioned upstream of the bladed impeller.
- As an alternative, it may be arranged in the diffuser.
- Another variant involves simultaneously installing a regulating member upstream of the compression stage and a regulating member in the diffuser.
- According to yet another feature, the motorcompressor unit further comprises an electronic control unit external to the casing and connected to the control motor by supply and control cables that pass through the casing at fluidtight lead-throughs.
- Other objects, features and advantages of the invention will become apparent from reading the following description, given solely by way of nonlimiting example, and made with reference to the attached drawings, in which:
-
FIG. 1 is a schematic view showing the overall design of a single-stage compressor unit; -
FIG. 2 is a detailed view of the compressor unit ofFIG. 1 , showing the aerodynamic regulating member; -
FIG. 3 illustrates an embodiment variant of the compressor unit ofFIG. 2 ; and -
FIG. 4 is a curve showing the change in power and work developed by the compressor unit as a function of the admitted gas flow rate. - The motorcompressor unit illustrated in
FIG. 1 essentially comprises amotor 1, consisting for example of a variable-speed electric motor driving the rotation of arotor 2, which itself at the same speed drives a drivenshaft 3 on which abladed impeller 4 is mounted. - As can be seen, the motorcompressor unit thus comprises a single compression stage consisting of the centrifugal
bladed impeller 4 which draws in a gas which is delivered from asupply pipe 5 in order to increase its pressure and deliver it atoutlet 5′. - In the embodiment depicted, the
rotor 2 is supported by twoend bearings shaft 3 which is likewise supported by twoend bearings rotor 2 and the drivenshaft 3 are connected by aflexible coupling 10. - However, it would not constitute a departure from the scope of the invention if the rotor and the driven shaft were to be connected by a fixed coupling. In such a case, one of the bearings such as 7 and 8 could be omitted.
- However, the arrangement depicted is advantageous because it considerably simplifies the assembly of the compressor unit by, in particular, eliminating the problems of aligning the rotor with the driven shaft.
- It may also be seen that the motorcompressor unit is also provided with a thrust bearing 11 that limits the axial movement of the driven
shaft 3 under the action of the rotation of theimpeller 4. - Finally, the assembly, which means to say the
motor 1 and the compression stage, is arranged in acommon casing 12 which is sealed against the gas handled by the compressor. In other words, themotor 1 here is at the intake pressure of the motorcompressor unit. -
FIG. 2 depicts a detailed view of the motorcompressor unit ofFIG. 1 . - This figure shows the
gas intake orifice 5 via which the gas to be compressed is drawn in in the direction of the arrow F, and theimpeller 4 which actually compresses the gas in order to deliver it, downstream, to a diffuser D in which the gas is slowed down in order to increase its pressure before it is delivered at outlet. - Upstream of the
impeller 4, the compressor is provided with a regulating member, referenced 13, produced in the form of a vane mounted across a diameter of agas passage 14 running between theintake orifice 5 and theimpeller 4. This vane constitutes an aerodynamic element which makes it possible to control the angle of the flow and keep it optimum over a wide range of flow rates. As will be seen, thisvane 13 is mounted on acontrol rod 15 which is turned by acontrol motor 16, for example a stepping motor incorporated into the motorcompressor, which means to say arranged inside thecommon casing 12. Themotor 16 is electrically powered from outside the motorcompressor and is operated by a central control unit (not depicted) which causes the motor to turn and accordingly orients thevane 13 in thepassage 14 in such a way as to shift the operating curve of the motorcompressor. - Of course, the supply and control cables that connect the control motor and the central control unit pass through the
casing 12 at lead-throughs (not depicted) that are sealed against the gas handled by the motorcompressor in such a way as to maintain a level of sealing that is far superior to the seals required at the penetrations for the mechanical devices according to the state of the art, when the motor is located outside the casing. - It will be noted that the compression stage comprises, in succession, between the
inlet 5 and theoutlet 5′, a supply zone A, thecentrifugal impeller 4 and the diffuser D. It will be noted that theaerodynamic member 13 here is positioned upstream of theimpeller 4. It would also be possible, according to the variant illustrated inFIG. 3 , for it to be situated in the region of the diffuser. - With reference to
FIG. 4 , which depicts the change in work developed by the compressor (curves a, b, c) on the one hand, and in the performance (curves a′, b′ and c′) on the other, as a function of the flow rate admitted at inlet to the motorcompressor unit, it is possible to maximize the aerodynamic performance of the compressor by using the variable pitch setting thereby enjoying a wider range of flow rates. - In particular, in terms of the developed work, starting out from an original position (curve a) in which the
vane 13 extends across the overall axis of the flow passage of gas through the compressor, it is possible, by varying the angular position of the vane, to modify the angle of the gaseous flow and thereby modify the flow rate for the same pressure value. - In other words, it is found that modifying the angle of incidence of the gaseous flow allows the operating curve of the compressor to be shifted translationally, thereby adapting its operating range.
- Moreover, the
motor 1 and thecompression stage 3 are arranged in one and thesame casing 12 that is sealed against the gas being handled, which means that the inside of the motorcompressor unit, particularly themotor 1 and at least thecompression stage 3, are immersed in the gas that is being handled, at the pressure of the gas entering via thesupply pipe 5. The inside of the motorcompressor has no shaft output sealing packing because the shafts bearing themotor 1 and bearing thebladed impeller 4, and the bearings that support them, are fully contained within the casing. The motorcompressor unit has only rotary seals subjected to small pressure differences, for example seals of the labyrinth seal type. No leak of process gas to the atmosphere can therefore occur, because the openings in the casing are confined to thegas supply pipe 5, thegas outlet pipe 5′, the lead-throughs for the cables that control and power themotors motor 1 is subject to the intake pressure set up at thesupply pipe 5. A circulation of gas can moreover be set up in order to cool it. - One particularly advantageous application of the invention is in gas transfer stations in which the pressure ratios that have to be developed between the intake and delivery sides are relatively small, notably below 2, and for which the motorcompressor units are preferably single-stage units or, in general, comprise fewer than three stages. Specifically, for this type of application, it is often desirable to have a relatively wide range of flow rates so that small or large flow rates can be offered.
- However, of course, any other application in which it is desirable to have a relatively wide range of flow rates may also be envisaged.
- It will moreover be noted that the use of an aerodynamic member for controlling the angle of incidence of the gas flow is advantageous for motorcompressor units comprising from 1 to 3 compression stages. However, such a member may advantageously be installed in single-stage motorcompressor units. However, when using a multi-stage compressor, the aerodynamic member can be mounted either on the first compression stage or on all the stages.
- As indicated earlier, the aerodynamic member can be mounted either at the inlet to the compression bladed impeller, so as to modify the angle of incidence of the gas flow handled by the bladed impeller, or at the diffuser so as to modify the deceleration of the gas and thereby modify the operating range. It is also possible, according to another embodiment, to provide one aerodynamic regulating member upstream or at the inlet of the bladed impeller or, in other words, upstream of the compression stage, and one regulating member in the diffuser.
Claims (20)
1. A motorcompressor unit comprising at least one motor driving the rotation of a rotor and at least one compression stage comprising a set of bladed impellers mounted on a driven shaft the rotation of which is driven by the rotor, the ensemble comprising the motor and the or each compressor, being mounted in a common casing that is gastight with respect to the gas handled by the compressor unit, characterized in that at least one of the compression stages comprises at least one member for regulating the angle at which the gas flows to or from a bladed impeller of a compression stage and a motor for controlling the regulating means mounted in the common casing.
2. The motorcompressor unit according to claim 1 , characterized in that the regulating member comprises at least one vane arranged across a diameter of the gas passage.
3. The motorcompressor unit according to claim 1 , characterized in that it comprises between one and three compression stages, preferably one compression stage, at least one of the said stages being provided with the regulating member.
4. The motorcompressor unit according to claim 1 , characterized in that each compression stage comprises, in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser, the regulating member being arranged upstream of the impeller.
5. The motorcompressor unit according to claim 1 , characterized in that each compression stage comprises, in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser, the regulating member being arranged in the diffuser.
6. The motorcompressor unit according to claim 1 , characterized in that each compression stage comprises in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser, and in that it comprises a regulating member (13) arranged upstream of the impeller and a regulating member arranged in the diffuser.
7. The motorcompressor unit according to claim 1 , characterized in that it further comprises an electronic control unit external to the casing and connected to the motor by supply and control cables that pass through the casing at fluidtight lead-throughs.
8. The motorcompressor unit according to claim 1 , in which the motor and the compression stage are arranged in the casing in such a way that the motor, and at least part of a bladed impeller of the compression stage, are subjected to the same pressure of gas entering the compression stage.
9. The motorcompressor unit according to claim 1 , configured to provide a pressure ratio lower than 2 between the intake and the delivery.
10. The motorcompressor unit according to claim 1 , capable of operating at an inlet pressure of 60 bar or higher.
11. The motorcompressor unit according to claim 2 , characterized in that it comprises between one and three compression stages, preferably one compression stage, at least one of the said stages being provided with the regulating member.
12. The motorcompressor unit according to claim 2 , characterized in that each compression stage comprises, in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser, the regulating member being arranged upstream of the impeller.
13. The motorcompressor unit according to claim 2 , characterized in that each compression stage comprises, in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser, the regulating member being arranged in the diffuser.
14. The motorcompressor unit according to claim 2 , characterized in that each compression stage comprises in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser, and in that it comprises a regulating member arranged upstream of the impeller and a regulating member arranged in the diffuser.
15. The motorcompressor unit according to claim 2 , characterized in that it further comprises an electronic control unit external to the casing and connected to the motor by supply and control cables that pass through the casing at fluidtight lead-throughs.
16. The motorcompressor unit according to claim 3 , characterized in that each compression stage comprises, in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser, the regulating member being arranged upstream of the impeller.
17. The motorcompressor unit according to claim 3 , characterized in that each compression stage comprises, in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser, the regulating member being arranged in the diffuser.
18. The motorcompressor unit according to claim 3 , characterized in that each compression stage comprises in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser, and in that it comprises a regulating member arranged upstream of the impeller and a regulating member arranged in the diffuser.
19. The motorcompressor unit according to claim 3 , characterized in that it further comprises an electronic control unit external to the casing and connected to the motor by supply and control cables that pass through the casing at fluidtight lead-throughs.
20. The motorcompressor unit according to claim 4 , characterized in that it further comprises an electronic control unit external to the casing and connected to the motor by supply and control cables that pass through the casing at fluidtight lead-throughs.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1061391A FR2970044B1 (en) | 2010-12-31 | 2010-12-31 | MOTOCOMPRESSOR GROUP WITH VARIABLE AERODYNAMIC PROFILE. |
FR1061391 | 2010-12-31 |
Publications (2)
Publication Number | Publication Date |
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US20120171056A1 true US20120171056A1 (en) | 2012-07-05 |
US10280938B2 US10280938B2 (en) | 2019-05-07 |
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Application Number | Title | Priority Date | Filing Date |
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US13/339,389 Active US10280938B2 (en) | 2010-12-31 | 2011-12-29 | Motorcompressor unit with variable aerodynamic profile |
Country Status (5)
Country | Link |
---|---|
US (1) | US10280938B2 (en) |
EP (1) | EP2472126B1 (en) |
CN (1) | CN102619766A (en) |
FR (1) | FR2970044B1 (en) |
PL (1) | PL2472126T3 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103511351A (en) * | 2013-10-08 | 2014-01-15 | 无锡杰尔压缩机有限公司 | Direct driving type pressure expanding guide vane adjusting device |
Citations (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2770106A (en) * | 1955-03-14 | 1956-11-13 | Trane Co | Cooling motor compressor unit of refrigerating apparatus |
US3160392A (en) * | 1962-01-05 | 1964-12-08 | David U Hunter | Turbine with variable nozzle |
US4027997A (en) * | 1975-12-10 | 1977-06-07 | General Electric Company | Diffuser for a centrifugal compressor |
US4219305A (en) * | 1978-12-26 | 1980-08-26 | Carrier Corporation | Diffuser control |
US4257733A (en) * | 1978-12-26 | 1981-03-24 | Carrier Corporation | Diffuser control |
US4460310A (en) * | 1982-06-28 | 1984-07-17 | Carrier Corporation | Diffuser throttle ring control |
US4503684A (en) * | 1983-12-19 | 1985-03-12 | Carrier Corporation | Control apparatus for centrifugal compressor |
US4877369A (en) * | 1988-02-08 | 1989-10-31 | Dresser-Rand Company | Vaned diffuser control |
US5452986A (en) * | 1994-01-12 | 1995-09-26 | Dresser-Rand Company | Vaned diffuser |
US5618160A (en) * | 1994-05-23 | 1997-04-08 | Ebara Corporation | Turbomachinery with variable angle fluid guiding devices |
US5683223A (en) * | 1994-05-19 | 1997-11-04 | Ebara Corporation | Surge detection device and turbomachinery therewith |
US5873696A (en) * | 1994-12-28 | 1999-02-23 | Ebara Corporation | Turbomachinery having variable angle flow guiding device |
US5895204A (en) * | 1997-08-06 | 1999-04-20 | Carrier Corporation | Drive positioning mechanism for a variable pipe diffuser |
US5947680A (en) * | 1995-09-08 | 1999-09-07 | Ebara Corporation | Turbomachinery with variable-angle fluid guiding vanes |
US6129511A (en) * | 1998-10-27 | 2000-10-10 | Carrier Corporation | Method and apparatus for controlling interaction between variable guide vanes and variable diffuser of a centrifugal compressor |
US6506011B1 (en) * | 2001-09-21 | 2003-01-14 | Carrier Corporation | Method for limiting split ring diffuser travel |
US20050223737A1 (en) * | 2002-02-28 | 2005-10-13 | Turbocor, Inc. | Centrifugal compressor |
US7144226B2 (en) * | 2003-03-10 | 2006-12-05 | Thermodyn | Centrifugal compressor having a flexible coupling |
US20090196741A1 (en) * | 2008-02-06 | 2009-08-06 | Minoru Tsukamoto | Turbo compressor and refrigerator |
US20090205360A1 (en) * | 2008-02-20 | 2009-08-20 | Haley Paul H | Centrifugal compressor assembly and method |
US20100172753A1 (en) * | 2009-01-08 | 2010-07-08 | Frank Lin | Compressor side inlet with improved aerodynamic performance and reduced manufacturing complexity |
US7824148B2 (en) * | 2004-07-13 | 2010-11-02 | Carrier Corporation | Centrifugal compressor performance by optimizing diffuser surge control and flow control device settings |
US20130272864A1 (en) * | 2010-12-10 | 2013-10-17 | Toyota Jidosha Kabushiki Kaisha | Centrifugal compressor |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IL109967A (en) * | 1993-06-15 | 1997-07-13 | Multistack Int Ltd | Compressor |
US7588415B2 (en) * | 2005-07-20 | 2009-09-15 | United Technologies Corporation | Synch ring variable vane synchronizing mechanism for inner diameter vane shroud |
NO324577B1 (en) * | 2005-11-11 | 2007-11-26 | Norsk Hydro Produksjon As | Pressure and leakage control in rotary compression equipment |
US8156757B2 (en) * | 2006-10-06 | 2012-04-17 | Aff-Mcquay Inc. | High capacity chiller compressor |
EP2006494A1 (en) * | 2007-06-20 | 2008-12-24 | ABB Turbo Systems AG | Drive for a pre-twist guide device |
-
2010
- 2010-12-31 FR FR1061391A patent/FR2970044B1/en not_active Expired - Fee Related
-
2011
- 2011-12-23 EP EP11195670.2A patent/EP2472126B1/en active Active
- 2011-12-23 PL PL11195670T patent/PL2472126T3/en unknown
- 2011-12-29 US US13/339,389 patent/US10280938B2/en active Active
- 2011-12-31 CN CN2011104632401A patent/CN102619766A/en active Pending
Patent Citations (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2770106A (en) * | 1955-03-14 | 1956-11-13 | Trane Co | Cooling motor compressor unit of refrigerating apparatus |
US3160392A (en) * | 1962-01-05 | 1964-12-08 | David U Hunter | Turbine with variable nozzle |
US4027997A (en) * | 1975-12-10 | 1977-06-07 | General Electric Company | Diffuser for a centrifugal compressor |
US4219305A (en) * | 1978-12-26 | 1980-08-26 | Carrier Corporation | Diffuser control |
US4257733A (en) * | 1978-12-26 | 1981-03-24 | Carrier Corporation | Diffuser control |
US4460310A (en) * | 1982-06-28 | 1984-07-17 | Carrier Corporation | Diffuser throttle ring control |
US4503684A (en) * | 1983-12-19 | 1985-03-12 | Carrier Corporation | Control apparatus for centrifugal compressor |
US4877369A (en) * | 1988-02-08 | 1989-10-31 | Dresser-Rand Company | Vaned diffuser control |
US5452986A (en) * | 1994-01-12 | 1995-09-26 | Dresser-Rand Company | Vaned diffuser |
US5683223A (en) * | 1994-05-19 | 1997-11-04 | Ebara Corporation | Surge detection device and turbomachinery therewith |
US5618160A (en) * | 1994-05-23 | 1997-04-08 | Ebara Corporation | Turbomachinery with variable angle fluid guiding devices |
US5873696A (en) * | 1994-12-28 | 1999-02-23 | Ebara Corporation | Turbomachinery having variable angle flow guiding device |
US5947680A (en) * | 1995-09-08 | 1999-09-07 | Ebara Corporation | Turbomachinery with variable-angle fluid guiding vanes |
US5895204A (en) * | 1997-08-06 | 1999-04-20 | Carrier Corporation | Drive positioning mechanism for a variable pipe diffuser |
US6129511A (en) * | 1998-10-27 | 2000-10-10 | Carrier Corporation | Method and apparatus for controlling interaction between variable guide vanes and variable diffuser of a centrifugal compressor |
US6506011B1 (en) * | 2001-09-21 | 2003-01-14 | Carrier Corporation | Method for limiting split ring diffuser travel |
US20050223737A1 (en) * | 2002-02-28 | 2005-10-13 | Turbocor, Inc. | Centrifugal compressor |
US7144226B2 (en) * | 2003-03-10 | 2006-12-05 | Thermodyn | Centrifugal compressor having a flexible coupling |
US7824148B2 (en) * | 2004-07-13 | 2010-11-02 | Carrier Corporation | Centrifugal compressor performance by optimizing diffuser surge control and flow control device settings |
US20090196741A1 (en) * | 2008-02-06 | 2009-08-06 | Minoru Tsukamoto | Turbo compressor and refrigerator |
US20090205360A1 (en) * | 2008-02-20 | 2009-08-20 | Haley Paul H | Centrifugal compressor assembly and method |
US20100172753A1 (en) * | 2009-01-08 | 2010-07-08 | Frank Lin | Compressor side inlet with improved aerodynamic performance and reduced manufacturing complexity |
US20130272864A1 (en) * | 2010-12-10 | 2013-10-17 | Toyota Jidosha Kabushiki Kaisha | Centrifugal compressor |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103511351A (en) * | 2013-10-08 | 2014-01-15 | 无锡杰尔压缩机有限公司 | Direct driving type pressure expanding guide vane adjusting device |
Also Published As
Publication number | Publication date |
---|---|
CN102619766A (en) | 2012-08-01 |
FR2970044A1 (en) | 2012-07-06 |
EP2472126A1 (en) | 2012-07-04 |
US10280938B2 (en) | 2019-05-07 |
FR2970044B1 (en) | 2013-02-01 |
PL2472126T3 (en) | 2014-09-30 |
EP2472126B1 (en) | 2014-03-19 |
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